为了降低发动机对声爆的影响，国内外新近低声爆超声速民机的气动布局以翼上发动机或尾吊发动机布局为主，然而翼上/尾吊发动机布局未充分利用超声速飞行器飞发一体化效应，对整机升阻比不利，现有文献中对发动机翼下布局声爆特性的研究不够充分。本文尝试采用一体化设计思想设计发动机翼下布局，以三维内转进气道作为超声速民机发动机的流量捕获装置，通过调整进气道外罩前缘曲线和外罩捕获面形状调控声爆，并通过“BoomProp”程序预测分析发动机几何参数及安装前后位置对超声速民机声爆特性影响，得到了可以通过优化外罩前缘曲线、发动机外罩捕获面形状参数以及改变发动机安装位置降低整机声爆的结论。
To mitigate the impact of engines on sonic booms, the aerodynamic layouts of recent low-boom supersonic civil aircraft, both domestically and internationally, primarily adopt either over-wing or tail-sitting engine layouts. However, these layouts exploit the integrated design effects of supersonic aircraft and engines insufficiently, adversely affecting the overall lift to drag ratio of the aircraft. Existing researches on the influence of engines on sonic booms are also inadequate. This paper at-tempts to adopt an integrated design concept to devise an under-wing engine layout, utilizing a three-dimensional inward turning inlet as the flow capture device for the integrated design of supersonic civil aircraft and engines, and controlling the sonic boom by adjusting the leading-edge curve and the shape parameters of cowl. The “BoomProp” program is utilized to predict and analyze the impact of engine geometric parameters and the installation positions of engine on the sonic boom characteristics of supersonic civil aircraft. While the conclusion has been reached that the sound boom of the overall model could be reduced by optimizing the leading-edge curve, the shape parameters of the cowl, and changing the installation position of the engine.
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